Free Turbine Generator For Aircraft

Abstract

A turbine engine for an aircraft is disclosed. The turbine includes a turbine generator which is not connected to the low or high pressure spools of the turbine engine. The generator is used to create power for use in electrical systems in the aircraft. In some embodiments, the free-turbine airfoils receive the core air through an array of variable-pitch vanes. The pitch of these vanes is alterable to control the core air so that the speed of the free turbine remains substantially constant even though engine speed fluctuates.

1 . An engine for an aircraft incorporating a turbine system comprising:
 a power-supply arrangement, said arrangement comprising a stage of airfoils disposed in a location such that said airfoils are dynamically engaged by a source of airflow in the turbine engine to cause said airfoils to rotate about a shaft and thus create mechanical energy in said shaft;   a power conversion device for converting the mechanical energy in said shaft into a useful energy source for the purpose of operating at least one power-consuming subsystem in the aircraft;   said stage of airfoils and said shaft rotating independently from all of the turbine-driving and thrust-producing shafts in the engine; and   said engine being adapted such that it primarily produces thrust by forcing air through at least one nozzle.   
     
     
         2 . The engine of  claim 1  comprising wherein said engine is one of a turbofan and a turbojet. 
     
     
         3 . The engine of  claim 1  wherein said power conversion device comprises an electrical generator, and said power-consuming subsystem comprises at least one electricity-consuming device. 
     
     
         4 . A gas-powered turbine engine comprising:
 a free turbine, said free turbine including a plurality of blades, said free turbine receiving a source of air through an array of variable-pitch vanes, said pitch being alterable to control the angular velocity of said free turbine at a substantially constant speed even when one of said engine speed or electrical power demand fluctuates;   means to convert mechanical energy from said free turbine into a source of power to operate a system in an aircraft;   said engine being adapted such that its primary energy production is of thrust by forcing air through at least one nozzle to propel said aircraft.   
     
     
         5 . The engine of  claim 4  incorporated into one of a turbofan and a turbojet. 
     
     
         6 . A gas-powered turbine engine comprising:
 a free turbine, said free turbine including a plurality of blades;   said free turbine receiving a source of air through an array of corresponding vanes;   one of said plurality of blades and said plurality of vanes being pitch-alterable in order to enable said free turbine to operate at a substantially constant angular velocity when one of said engine speed or electrical power demand fluctuates;   means to convert mechanical energy from said free turbine into a source of power to operate a system in an aircraft; and   said engine being adapted such that its primary energy production is of thrust by forcing air through at least one nozzle to propel said aircraft.   
     
     
         7 . The gas-powered turbine engine of  claim 6  wherein said free turbine has a shaft which rotates independently from all of the turbine-driving and thrust-producing shafts in the engine. 
     
     
         8 . The gas-powered turbine engine of  claim 6  wherein gas-powered turbine engine is an aircraft engine. 
     
     
         9 . The gas-powered turbine engine of  claim 6  wherein said gas-powered turbine engine primarily produces thrust by forcing air through a nozzle.